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On The Hypersonic Flow Over A Delta Wing With Very Supersonic Leading Edges
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Book Synopsis On the Hypersonic Flow Over a Delta Wing with Very Supersonic Leading Edges by : Norman D. Malmuth
Download or read book On the Hypersonic Flow Over a Delta Wing with Very Supersonic Leading Edges written by Norman D. Malmuth and published by . This book was released on 1965 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt: For the case of very supersonic leading edges, the inviscid hypersonic flow over the windward side of a symmetrical flat-plate delta wing at incidence is analyzed. The limit selected is that the incidence is of higher order than the aspect ratio as the incidence tends to zero at infinite Mach number. In this framework, the flow regions consist of a two-dimensional domain adjacent to the leading edges and a central conefield. The flow quantities in the central region represent small linear, rotational perturbations about the zero sweep flow. A Riemann-Poincare boundary value problem for the pressure perturbation is formulated. An additional condition involving the sidewash at the shock is found to be required to resolve the indeterminacy of the foregoing boundary value problem. Series solutions and numerical results are presented for the shock shape and the pressure. The behavior of the latter quantity is found to be similar to that given by the irrotational linear solution for the supersonic leading edge case. Finally, the relationship between the present application and others involving diffraction problems and corner flows is indicated.
Book Synopsis On the Hypersonic Flow Over a Delta Wing with Very Supersonic Leading Edges by : Norman D. Malmuth
Download or read book On the Hypersonic Flow Over a Delta Wing with Very Supersonic Leading Edges written by Norman D. Malmuth and published by . This book was released on 1965 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis On the Hypersonic Flow Past Blunted, Flat Delta Wings by : Arnold Polak
Download or read book On the Hypersonic Flow Past Blunted, Flat Delta Wings written by Arnold Polak and published by . This book was released on 1970 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: The flow of a perfect gas over the slab portion of a blunted delta wing flying at hypersonic speeds is studied. A set of approximate equations is derived and a solution - for an inviscid flow - is obtained. Using this solution as a representation for the inviscid flow problem, a formulation to the laminar boundary-layer equations is presented; one which is applicable to the flow field's azimuthal planes where the crossflow gradients are not too large. Numerical solutions to these boundary-layer equations have been obtained; however, these are restricted to the azimuthal planes and near to the leading edges. The results indicate the presence of a dividing surface streamline since a numerical solution could not be obtained near the centerplane of the wing, where the crossflow velocity is large. (Author).
Book Synopsis Research on Hypersonic Flow of Blunt Delta Wings. Part I. Theoretical and Experimental Study of a 70-degree Blunt Delta Wing for Low Angles of Attack at Supersonic and Hypersonic Speeds by : Bernard Mazelsky
Download or read book Research on Hypersonic Flow of Blunt Delta Wings. Part I. Theoretical and Experimental Study of a 70-degree Blunt Delta Wing for Low Angles of Attack at Supersonic and Hypersonic Speeds written by Bernard Mazelsky and published by . This book was released on 1967 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt: The object of the present analysis is to investigate the high-speed aerodynamic properties of a blunt delta wing at low angles of attack where the maximum lift to drag ratio occurs. Oguchi's solution of hypersonic flow over a blunt leading edge flat plate at zero incidence is extended to three dimensional delta wings at angle of attack. The shock wave shapes and pressure distributions were obtained by employing the oblique shock relations at the windward sides of the Prandtl-Meyer equations at the leeward side of the wing. The total lift and drag of the wing due to pressure and skin friction were computed by numerical integration using the IBM 7094 computer. The present calculated aerodynamic forces generally agree with the experimental data at the high supersonic Mach numbers (M approx.> or = 4) and lower thickness ratio of the wing which is a 70-degree swept slab sided delta wing with a cylindrical leading edge. (Author).
Book Synopsis Numerical Simulation of Hypersonic Flow Over a Blunt Leading Edge Delta Wing by : Kuok-Ming Lee
Download or read book Numerical Simulation of Hypersonic Flow Over a Blunt Leading Edge Delta Wing written by Kuok-Ming Lee and published by . This book was released on 1989 with total page 138 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Calculation of Supersonic Viscous Flow Over Delta Wings with Sharp Subsonic Leading Edges by : Y. C. Vigneron
Download or read book Calculation of Supersonic Viscous Flow Over Delta Wings with Sharp Subsonic Leading Edges written by Y. C. Vigneron and published by . This book was released on 1978 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Leeward Flow Over Delta Wings at Supersonic Speeds by :
Download or read book Leeward Flow Over Delta Wings at Supersonic Speeds written by and published by . This book was released on 1980 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Numerical Solution of Supersonic and Hypersonic Viscous Flow Fields Around Thin Planar Delta Wings by : Guion Stewart Bluford (Jr.)
Download or read book A Numerical Solution of Supersonic and Hypersonic Viscous Flow Fields Around Thin Planar Delta Wings written by Guion Stewart Bluford (Jr.) and published by . This book was released on 1978 with total page 233 pages. Available in PDF, EPUB and Kindle. Book excerpt: A numerical technique was used to compute the supersonic and hypersonic, viscous flow fields around thin planar delta wings. These solutions were obtained by solving the Navier-Stokes equations subject to a conical approximation. The integration technique used was the MacCormack finite-difference scheme. Solutions were obtained for the upper-only, lower-only, and total flow fields around delta wings with supersonic leading edges. These solutions span a Mach number range of 2.94 to 10.17, a local Reynolds number range of 334,500 to 5,000,000, and various angles of attack from -15 to +15 deg. A stability criteria was developed and used which accounted for both the viscous and inviscid flow regions. Good agreement was obtained between the numerical results and experimental flow field data. The shock-induced vortex within the viscous region and the hypersonic viscous bubble on top of the boundary layer were computed, for the first time. A unique examination was made of the vortical singularities in the conical cross-flow plane of the delta wing. This investigation demonstrated the feasibility of applying the conical approximation to the Navier-Stokes equations in order to solve flow fields around thin delta wings.
Book Synopsis An Experimental Study of the Pressure and Heat-transfer Distribution on a 70° Sweep Slab Delta Wing in Hypersonic Flow by : Mitchel H. Bertram
Download or read book An Experimental Study of the Pressure and Heat-transfer Distribution on a 70° Sweep Slab Delta Wing in Hypersonic Flow written by Mitchel H. Bertram and published by . This book was released on 1963 with total page 136 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented for a study of the pressure and heat-transfer distributions and force characteristics of slab delta wings of 70° sweep at Mach numbers of 6.8 and 9.6 in air and 18 in helium. The wings had cylindrical leading edges and were tested with two different noses. One was sharp in plan view and the other was a tangent sphere with the same diameter as the cylindrical leading edge. Simple approaches to predicting the heat transfer are shown to be successful if the flow pattern peculiar to the angle-of-attack range under consideration is taken into account.
Book Synopsis Theoretical and Experimental Longitudinal Aerodynamic Characteristics of an Aspect Ratio 0.25 Sharp-edge Delta Wing at Subsonic, Supersonic, and Hypersonic Speeds by : Charles H. Fox
Download or read book Theoretical and Experimental Longitudinal Aerodynamic Characteristics of an Aspect Ratio 0.25 Sharp-edge Delta Wing at Subsonic, Supersonic, and Hypersonic Speeds written by Charles H. Fox and published by . This book was released on 1974 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: The suction analogy concept of Polhamus for predicting vortex lift in conjunction with an appropriate potential-flow solution is called the present method. This method is applied herein to an aspect ratio of 0.25 sharp-edge delta wing from a Mach number of 0.143 to 10.4 in free air and at 0.074 in ground effect, and also to an aspect ratio of 0.35 triangular cross-sectional body at Mach number of 6.9. The models had subsonic leading edges at the test Mach numbers. Vortex-flow effects could be neither confirmed nor denied to exist at high speeds because of the lack of flow visualization above a Mach number of 0.143. The data, however, could be better predicted by including a vortex-flow effect, although not always to the extent predicted from the present method because of the presence of actual and hypothesized unmodeled flow situations.
Book Synopsis Hypersonic Flow Over Delta Wings at High Angles of Attack by : Joseph L. Francis
Download or read book Hypersonic Flow Over Delta Wings at High Angles of Attack written by Joseph L. Francis and published by . This book was released on 1966 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Lee-side Flow Over Delta Wings at Supersonic Speeds by : David S. Miller
Download or read book Lee-side Flow Over Delta Wings at Supersonic Speeds written by David S. Miller and published by . This book was released on 1985 with total page 160 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer Measurements on a Delta Wing with Blunted Leading Edges in Hypersonic Flow by : Bo Lemcke
Download or read book Heat Transfer Measurements on a Delta Wing with Blunted Leading Edges in Hypersonic Flow written by Bo Lemcke and published by . This book was released on 1975 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Transonic and Supersonic Flow Past a 65° Delta Wing with Rounded Leading Edges by : Krishnaswami Yegna Narayan
Download or read book Transonic and Supersonic Flow Past a 65° Delta Wing with Rounded Leading Edges written by Krishnaswami Yegna Narayan and published by . This book was released on 1988 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Transonic and Supersonic Flow Past a 65° Delta Wing with Rounded Leading Edges by : Krishnaswami Yegna Narayan
Download or read book Transonic and Supersonic Flow Past a 65° Delta Wing with Rounded Leading Edges written by Krishnaswami Yegna Narayan and published by . This book was released on 1988 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Study of Lee-side Flows Over Conically Cambered Delta Wings at Supersonic Speeds by : Richard M. Wood
Download or read book Study of Lee-side Flows Over Conically Cambered Delta Wings at Supersonic Speeds written by Richard M. Wood and published by . This book was released on 1987 with total page 220 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Transonic and Supersonic Flow Past a 65 Degree Delta Wing with Rounded Leading Edges - Analysis of Experimental Data by : Krishnaswami Yegna Narayan
Download or read book Transonic and Supersonic Flow Past a 65 Degree Delta Wing with Rounded Leading Edges - Analysis of Experimental Data written by Krishnaswami Yegna Narayan and published by . This book was released on 1988 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
